Effects of sideslip angle, rudder deflection, and Mach number are presented for trim flight at altitudes from 40,000 to 70,000 ft and at Mach numbers from 0.70 to 2.08; comparisons made with simple theoretical methods of estimating loads; total directional stability for each aircraft as calculated by use of vertical tail loads is shown.


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    Title :

    Vertical-tail loads measured in flight on four airplane configurations at transonic and supersonic speeds


    Additional title:

    NASA -- Tech Note


    Contributors:
    Reed, R.D. (author)


    Publication date :

    1960


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :